A rotor blade for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil extending in span between a root region and a tip region and a tip portion extending at an angle from the tip region of the airfoil.

A compressor disc for a compressor of a gas turbine engine includes a circumferentially extending groove for receiving blade roots of a plurality of compressor blades. The circumferentially extending groove includes a planar surface offset into the groove.

A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.

A tip shroud includes a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading Z-notch of the tip shroud, and/or a downstream radially inner surface of a wing. The surface profiles may have a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table. The radially inner surface of the wing may define a protrusion extending along the radially outer end of the airfoil, the suction side fillet, and a radial inner surface of the wing to an axial edge of the wing.

The present invention relates to a stator of an axial compressor stage of a turbomachine featuring a radially outer blade ring forming an outer ring surface, a radially inner blade ring forming an inner ring surface, and several stator blades connected to the blade rings. It is provided that the outer ring surface and/or the inner ring surface has at least in a partial area a changing radius relative to a central axis of the stator both in the axial direction and in the circumferential direction.

An apparatus and method for flowing cooling air through an outer wall of an engine component such as an airfoil. The airfoil having the outer wall can include a skin layer and a porous layer. The skin layer can include a skin cooling circuit for providing the cooling air from an interior of the airfoil to the exterior of the airfoil through the porous layer.

The present invention relates to a rotor (1) of a turbomachine turbine, comprising a rotor disc (2) and a plurality of blades (3) distributed at its periphery, said rotor disc (2) comprising a plurality of mainly axial cells (23), each blade (3) comprising a root (32), retained in one of the cells (23) of said rotor disc, each root being dimensioned so as to form a space (4) between the bottom of the cell (23) and the radially inner face (324) of the root. This rotor is remarkable in that said root comprises a mainly axial blind hole (5) opening onto the upstream face of the root and a plurality of mainly radial air ejection orifices (6), each air ejection orifice (6) opening into said blind hole (5) and onto the radially inner face (324) of the root located facing the bottom of the cell (23).

Disclosed are a fan motor and a vacuum cleaner which include a blowing fan and a plurality of diffuser blades disposed at a radially outer side of the blowing fan and circumferentially spaced apart from each other. Outer end portions of the plurality of diffuser blades include a spoiler portion formed obliquely to an outward direction with respect to an extending direction of the diffuser blades, so that a flow separation of air flowing across an outer surface of the diffuser blade is reduced. Accordingly, the suction force of the fan motor increases.

A centrifugal compressor having a stator which is designed as an inlet stator, in particular for a compressor, with at least one vane having a vane airfoil around which a fluid can flow, with a plurality of vanes arranged in the form of a ring, with an adjustment device for adjusting the vane, wherein a curvature of a profile center line of the vane airfoil has at least one inflection point.

A rotor for an engine is provided. The rotor comprising a rotor base part that has fastening grooves for rotor blades that are arranged in succession around a rotational axis along a circumferential direction, multiple rotor blades that are respectively supported in a form-fit manner inside a corresponding fastening groove by means of a blade root, and at least one securing element for the axial securing—with respect to a rotational axis—of at least one of the rotor blades at the rotor base part. The at least one securing element has two edges that are arranged at a radial distance to one another and through which the securing element is supported in a form-fit manner at the rotor base part, on the one hand, and, on the other hand, at the at least one rotor blade.